Bambino 6 (bambino6-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: Bambino 6 (bambino6-il) Reynolds number: 200,000 Max Cl/Cd: 36.25 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-bambino6-il-200000-n5.txt Download as CSV file: xf-bambino6-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Bambino 6
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4904 0.08852 0.08526 -0.0438 1.0000 0.0134
-10.500 -0.5225 0.07999 0.07683 -0.0477 1.0000 0.0133
-10.250 -0.5707 0.06965 0.06662 -0.0540 1.0000 0.0130
-9.750 -0.7887 0.04260 0.03890 -0.0430 1.0000 0.0094
-9.500 -0.7938 0.03853 0.03449 -0.0408 0.9968 0.0099
-9.250 -0.7826 0.03505 0.03060 -0.0406 0.9913 0.0104
-9.000 -0.7656 0.03225 0.02742 -0.0405 0.9863 0.0111
-8.750 -0.7471 0.03010 0.02492 -0.0400 0.9803 0.0121
-8.500 -0.7261 0.02786 0.02227 -0.0398 0.9759 0.0131
-8.250 -0.7076 0.02602 0.02009 -0.0385 0.9696 0.0137
-8.000 -0.6837 0.02419 0.01799 -0.0384 0.9647 0.0159
-7.750 -0.6587 0.02322 0.01689 -0.0380 0.9587 0.0189
-7.500 -0.6311 0.02220 0.01567 -0.0380 0.9534 0.0228
-7.000 -0.5736 0.02159 0.01482 -0.0383 0.9431 0.0333
-6.750 -0.5433 0.02178 0.01495 -0.0388 0.9381 0.0373
-6.500 -0.5097 0.02147 0.01433 -0.0398 0.9347 0.0416
-6.250 -0.4867 0.02130 0.01416 -0.0389 0.9267 0.0447
-6.000 -0.4549 0.02132 0.01409 -0.0397 0.9217 0.0489
-5.750 -0.4249 0.02087 0.01340 -0.0400 0.9159 0.0522
-5.500 -0.3941 0.02021 0.01250 -0.0404 0.9095 0.0535
-5.250 -0.3560 0.01900 0.01118 -0.0426 0.9055 0.0551
-5.000 -0.3253 0.01823 0.01037 -0.0432 0.8976 0.0566
-4.750 -0.2886 0.01754 0.00962 -0.0450 0.8913 0.0588
-4.500 -0.2562 0.01700 0.00898 -0.0459 0.8829 0.0618
-4.250 -0.2191 0.01642 0.00828 -0.0477 0.8754 0.0645
-4.000 -0.1872 0.01595 0.00771 -0.0484 0.8652 0.0662
-3.750 -0.1540 0.01523 0.00696 -0.0496 0.8548 0.0688
-3.500 -0.1218 0.01466 0.00636 -0.0505 0.8430 0.0718
-3.250 -0.0920 0.01426 0.00588 -0.0508 0.8300 0.0750
-3.000 -0.0643 0.01395 0.00548 -0.0507 0.8160 0.0780
-2.750 -0.0372 0.01366 0.00510 -0.0504 0.8000 0.0812
-2.500 -0.0131 0.01335 0.00472 -0.0495 0.7744 0.0858
-2.250 0.0098 0.01315 0.00434 -0.0482 0.7291 0.0918
-1.750 0.0513 0.01305 0.00405 -0.0448 0.6576 0.1333
-1.500 0.0737 0.01308 0.00396 -0.0436 0.6414 0.1481
-1.250 0.0958 0.01311 0.00386 -0.0423 0.6257 0.1602
-1.000 0.1172 0.01308 0.00378 -0.0409 0.6124 0.1691
-0.750 0.1385 0.01309 0.00371 -0.0395 0.5965 0.1770
-0.500 0.1599 0.01307 0.00364 -0.0381 0.5835 0.1836
-0.250 0.1805 0.01309 0.00358 -0.0365 0.5640 0.1901
0.000 0.2001 0.01308 0.00353 -0.0348 0.5428 0.1984
0.250 0.2189 0.01307 0.00348 -0.0329 0.5156 0.2120
0.500 0.2370 0.01300 0.00345 -0.0310 0.4904 0.2442
0.750 0.2502 0.01286 0.00343 -0.0280 0.4505 0.3191
1.000 0.2360 0.01166 0.00332 -0.0192 0.4292 0.6352
2.000 0.2687 0.01426 0.00480 -0.0028 0.0658 0.8880
2.250 0.2998 0.01449 0.00503 -0.0036 0.0638 0.8991
2.500 0.3369 0.01482 0.00538 -0.0057 0.0616 0.9103
2.750 0.3747 0.01526 0.00583 -0.0081 0.0574 0.9178
3.000 0.4090 0.01563 0.00620 -0.0099 0.0528 0.9235
3.250 0.4689 0.01630 0.00687 -0.0171 0.0481 0.9326
3.500 0.5066 0.01686 0.00739 -0.0196 0.0441 0.9387
3.750 0.5446 0.01711 0.00756 -0.0221 0.0393 0.9419
4.000 0.5719 0.01733 0.00775 -0.0223 0.0362 0.9444
4.500 0.6166 0.01793 0.00823 -0.0209 0.0177 0.9513
4.750 0.6478 0.01834 0.00868 -0.0221 0.0171 0.9538
5.000 0.6740 0.01876 0.00918 -0.0223 0.0163 0.9568
5.250 0.6928 0.01920 0.00973 -0.0209 0.0152 0.9593
5.500 0.7086 0.01959 0.01021 -0.0189 0.0148 0.9623
5.750 0.7257 0.02004 0.01074 -0.0174 0.0146 0.9645
6.000 0.7474 0.02062 0.01142 -0.0168 0.0144 0.9670
6.250 0.7627 0.02125 0.01215 -0.0150 0.0140 0.9700
6.500 0.7761 0.02180 0.01278 -0.0129 0.0139 0.9747
6.750 0.7966 0.02245 0.01348 -0.0123 0.0125 0.9780
7.000 0.8143 0.02302 0.01411 -0.0112 0.0125 0.9811
7.250 0.8326 0.02367 0.01481 -0.0102 0.0127 0.9858
7.500 0.8532 0.02436 0.01560 -0.0100 0.0129 0.9886
7.750 0.8734 0.02514 0.01646 -0.0097 0.0131 0.9921
8.000 0.8899 0.02595 0.01735 -0.0087 0.0138 0.9950
8.250 0.9153 0.02602 0.01744 -0.0090 0.0147 0.9972
8.500 0.9386 0.02637 0.01784 -0.0092 0.0156 0.9993
8.750 0.9464 0.02680 0.01832 -0.0065 0.0165 1.0000
9.250 0.9516 0.02785 0.01945 0.0009 0.0176 1.0000
9.500 0.9624 0.02817 0.01979 0.0032 0.0181 1.0000
9.750 0.9722 0.02869 0.02038 0.0054 0.0184 1.0000
10.000 0.9798 0.02948 0.02123 0.0077 0.0185 1.0000
10.250 0.9863 0.03047 0.02227 0.0100 0.0184 1.0000
10.500 0.9932 0.03148 0.02334 0.0121 0.0185 1.0000
10.750 1.0024 0.03238 0.02429 0.0138 0.0186 1.0000
11.000 1.0021 0.03412 0.02611 0.0162 0.0184 1.0000
11.250 1.0058 0.03559 0.02766 0.0180 0.0183 1.0000
11.500 1.0058 0.03746 0.02959 0.0198 0.0182 1.0000
11.750 1.0052 0.03948 0.03165 0.0214 0.0180 1.0000
12.000 0.9983 0.04222 0.03436 0.0233 0.0177 1.0000
12.250 0.9972 0.04463 0.03684 0.0247 0.0164 1.0000
12.500 1.0026 0.04642 0.03866 0.0256 0.0161 1.0000
12.750 1.0087 0.04824 0.04048 0.0265 0.0157 1.0000
13.000 1.0289 0.04923 0.04123 0.0277 0.0150 1.0000
13.250 1.0556 0.04984 0.04173 0.0283 0.0148 1.0000
13.500 1.1982 0.05078 0.04196 0.0201 0.0127 1.0000
13.750 1.1834 0.05216 0.04356 0.0238 0.0125 1.0000
14.000 1.1857 0.05377 0.04530 0.0254 0.0124 1.0000
14.250 1.1825 0.05558 0.04728 0.0273 0.0121 1.0000
14.500 1.1857 0.05762 0.04947 0.0285 0.0118 1.0000
14.750 1.1908 0.05964 0.05161 0.0294 0.0116 1.0000
15.000 1.2082 0.06208 0.05413 0.0296 0.0113 1.0000
15.250 1.4776 0.08231 0.07373 -0.0033 0.0101 1.0000
15.500 1.4698 0.08441 0.07607 0.0002 0.0101 1.0000
15.750 1.4509 0.08605 0.07797 0.0049 0.0101 1.0000
16.000 1.4371 0.08797 0.08011 0.0088 0.0101 1.0000
16.250 1.4094 0.08934 0.08173 0.0142 0.0101 1.0000
16.500 1.3937 0.09140 0.08394 0.0181 0.0101 1.0000
16.750 1.3738 0.09340 0.08612 0.0219 0.0101 1.0000
17.000 1.3522 0.09546 0.08835 0.0252 0.0101 1.0000
17.250 1.3272 0.09767 0.09074 0.0280 0.0101 1.0000
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Polar data table (+)
Polar graphs
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